Aircraft construction



July 10,` 1945. w. H. scHwEBEI.

AIRCRAFT CONSTRUCTION Filed March 1'7, 1941 2 Sheets-Sheet l INVENTOR- n lim-02mg July 1Y0, 1945. w. H. scHwEBEL 2,380,336

AIRCRAFT COIIS'IRUCTIION'V Filed March 17, 1941 v 2 Sheets-Sheet 2 l INVENTOR wlLLlAM H. scHwEBEl.

APatented July 10, 1945 l OFP-ICE CONSTRUCTION l Willis-in' n. scliwebi, Baldwin; N; y., asslgnor, by

'l lmesne assignments, tofWlliam BifScarborough,

Q Englewood,-N.`J.,as` trusteej y u Application Maschili, 1941, lseri'algin.rssa'lliz nfcla'imsll' (el.- ransom" l' y' This-invention relates to aircraft structure, and has .particular reference tous. geodeti'e'type of structure for airplane fuselages, wings, and the like, although the invention is not limited to that Geodetic structures for aircraft, particularly'for Tf-uselages, have proven very effective, not onlyby reason of; their' lightness andgreat strength, but lalso because they are substantiallyA immune .from damage: owing -v to the fact.- that the .load-.sunf- :porting membersthat are subject to damage form avery-*small proportion vof the areaofthev structure; By sway'v of illustration, the V:geodetlc type iis made collapsible; and .the additional Vnecessaryisupportingparts, such as Wing spars, lbulk-- heads, `and the like, are inserted. Either before or after'the structure is bondedfand stripped from vthe mandrel or form, a skin covering may be applied, as required, such as fabric, sheet -metal,

:wood veneer, iibre, or the like. Alternativelmthis skin cover maybe applied to the inner surfaceof theshell.A j ,i y It-will be 'seen'. that the geodetic structure of -thisqinvention is very inexpensive `to make, acy -cording tot the describedv method, and may be Y manufactured in large quantities with substantial ofl fuselagehas de1fnonstrat`editsrsubstantial'im;y

,munity to` injury by projectilesfsuch as machine v.gunlaulleta because nearly all ofthe exposedarea of the 'fuselage isioccupied by. theopeningswhich the. bullets! traverse, and ther chancey of striking oneofthe strength members is, practically re- '.mote. However, as constructed` atv the present time, geodetic fuselages are heavy and costly: and nlaborious `tol make, requiring the expenditure of janinordinateamountoftime. 1;;'

In accordance with the present invention, a geodetic aircraft structure, and the, method of ymaking the same are provided, ffwherebynot only .strong andy essentially rigid -structures'can be made, butthatcan be doneinexpensively of readvily available materials vin but asmall fraction of the time that is required to make geodeticstruc-` ltures of metallic shapesioined at theirjunction points by riveted clips or cleats.' j l,

Avpreferred embodiment of the 'inver'ltion comi prises an aircraft structure, suchas a fuselageor wing section, wound ofoverlapping `spaced 4strips of thinwood veneer on a mandrel'or form having n geodetic structure;

ing drawings, in which:

uniformity;,0f readily available and inexpensive -materials in avery short time; i vFor a morecomplete understanding of the inventiorrreference may be had to the accompany.-

i Figure y1 illustrates the method-of Winding the -wood strips in geodetic fashion lupon a rotatable the shape desired for the V'fuselage shell:- f

collapsible mandrel of Fig.12 illustrates an arrangement fory bonding theiwoodstrips together;

-'Fig. 3fis an enlarged detail of thejcrcss strip fkFig.V 4 is'an emerged section therethroughfas' seen along the line 4-4 of Fig. 3;

Fig. 5 is an enlarged section Figsc, 'l anais illustrate a modlfled' forni of, the method and apparatus o1' this invention.

Referring to Fig. l1, numeral I0 designates a -.mandrel having the predeterminedshape ofi the sul theshape 'ofthe iinished structure.' The strips v are wound on the mandrel or form so thatjthey cross at f an f anglaf preferably' '90?, to vrproducel .the

' characteristic' geodetic shape,l and alternate` strips A1 -overlap each other as vthey are wound in' direcj j *tions normal to'each other, until therequisite number ofplies are yso e'lrranged.v lnterposedvbetweenthe abutting Asurfaces of l these strips is an adhesive, preferably a dry thermo-'responsivefad--.

fihesive, suchv as athermoplastic yor thermosetting Isyntheticresin, thelatter being preferred. When.

1 the' winding operationl has' been completed, the 'f-wood stripping, `While ystill on "the mandrel or u1'orm,is"subjected to heat and pressure suchthat "fuselage to be formed and made of a plurality of i segmental elements II,V which jmay be moved radially relatively to each otherfto collapse inthe mandrel in accordance with well-known practice.

-This mandrel is preferably made of metalsuch las steel," and is light. in Weight. l It is mounted on thev shafvlz, which'is journaled 'in trunnion's l la suitably supported on the iloor'srofthat the man- '.drfelv I0 may be rotated 'about its longitudinal axis.

the adhesive fusesand bonds-- the abuttingsurlrlfac'es, together? into a unitary essentially. rigid -fstructure, having theaforementioned -characterf iistics.f=iThen' the finished structure is stripped 1 --from the mandrel or iorm, :which for thatvpurp'ose i vPreferably the engine bulkhead ring I4 is first made and slipped over the mandrel so vas to be propbulkheadrings, not shown, may be applied, al-

lof asfseen assembled to proper thickness and then bonded together into a unitary uninterrupted ring which accordingly must be slipped over the mandrel I before the latter is mounted on its trunnions. However, if desired, and that may be desirable with intermediate bulkhead rings, they may be interrupted ring segments fastened together when in positionon the mandrel. These rings I4 and I5 are temporarily secured to the mandrel I0, by cleats I6, or the like, which hold the bulkhead rings in place on the mandrel against rotation relatively thereto.

Rings I4 and Il5 serve as nailing bases, to which the ends of the thin, flat, flexible strips or ribbons are tacked .preparatory'to the winding yop- VVPreferably the strips are coated with a water f dispersion of the resin, which is then dried, so

eration. These ribbons or lstrips are preferably- I formed of straight-grained wood, such as birch,`

spruce, mahogany, or other suitable'natural Vma-V terial, or they may be formed of synthetic material, preferably including bres for strength, such as textile fibres' bound by phenolic resin, or so-called -iibre and the like. These ribbon strips have the width of approximately three inches, more or less, and arescarfed vor shaped along their longitudinal edges so as to taper down to a thin edge, from a maximum center thickness. on theorder ofsl -to 3/i of' an'inch, as is 'indicated in`Figs.f4 and 5. These'ribbons or strips should be long enough to encompass the entire mandrel from one` end to the' other, in order to'avoid piecing during the winding operation'. Aswood strips are not ordinarily obtain- 'ablev in that length from a single ditch, a, series of strips may be bonded together by suitable adhesive, such as thermosetting adhesive of the synthetic resin type, care being taken to so arrange Athe joints inthe strips that they, when Wound on the mandrel, are not superimposed. .Each strip is tacked to the engine bulkhead ring I 4 and'then wound diagonally around the mandrel I0, preferably at an angle of approximately 45 to the plane of the axis thereof', the mandrel 'meanwhile being slowly rotated by hand or power to facilitate the winding operation.` Guide/pins A -.I'l projecting from the mandrel I0 and spaced apart the width of the strips .and arranged in Lpairs in thedirection in which the strip is to be wound, serve to properly vguide thestrips in the .winding operation.

Beginning with the first: layerof strips I8,

'each is wound spirally around the mandrel as tightly'as possible, between the guide pins I1 from -the engine bulkhead ring I4, to which'it has been, tacked, tothe tail bulkheadv I5, to which it islikewise tacked.` This operation is repeated -for each 'strip I8 of the fuselage until the man- :drel IU is covered with parallel strips I8 all wound in the same direction.

. Afterthe rst layer of strips has beenthus wound, the second layer of strips I9 is'applied in the same way, but in adirection normal to the direction of theiirstlayer of` strips, so thatk the strips cross the' strips` I8 of the first layer and extend 45 to the-plane of the axis of the Inan- -drel. l. v

1 iThe spacing between the parallel strips I8 and i I9 in both directions depends upon the load that 'the structure is required to sustain. Thus, for a lsingle motor pursuit airplane, for example, car- .ryingja normal load, the spacing between adjacent strips may be on the order of four to six .inchesso thatthe openings in the geodetic structure thus formed are approximately four to six inches square. Obviously, the spacing. may be Whatever is required andthe angle between crossthat the outer or. exposed surface of each of the first strips I8 is coated with a layer of dry resin.

y The stripsv I8 ofthe first layer should lbe so coated with adhesive but the strips of the second layer I9 should not be so coated on the under surface since they engage those of the first layer only at the point of crossing and hence if coated all over, they might .adhere to the outer surface of the mandrel `IIJ A.andthus render removal of the completed'shell difficult.

' The third layer of `strips I8 is wound in the same direction of the first layer I8, so as to cross the strips. I9, and the fourth layer of strips I9 is wound in the same direction-as Vthe second layer I9 so yas to cross lthe thirdlayer I8.',Land so gn until the'requisite number Vof stripshave -been applied to produce Vthe desired thickness. Thus, for ordinary purposes, such as inthel case of aforementioned light plane, .five ory six strips may be wound in each direction so that the thickness of the strip between crossing pointszis on the order of a quarter "of 'an' inch, and'at crossing points `on', the order of a half-inch, due to the double layers at that point; The guide .pins 'I'I are extended from the mandrel I0 to a lengthapproximately equalto .the aggregate thickness of the strips at their crossing point, (but the pins I1 should not extend appreciably higher because they would interfere withthe bonding.v operation by holding therubberl bag from the strips,

as will be understood.

cluding' the strip whichA crosses in the normal direction; Because the strips. are scarfed to thinness along their .longitudinal .edges, kthey overlap `with no abruptnessatthe point .of crossging,Y as is indicated in Figs. 4 and 5, so that each ,rib when nishedisa smooth, rounded-lamina, `as shown. This Aedge scarring or shaping also `precludesI curling of the multiple-ply layer after bonding. i

After the winding' operation has been completed in the manner described, the'entire mandrel I0 isremoved from lits'trunnions I3 andenclosed in a rubber bag 20 lwhich is sealed over .the ends of themandrel `II) and fittedr with one ,or more vent pipes 2 I", as vshown inY Fig. 2. This assembly is thenl placed within'aY sealed `tank 22 with the kvent pipes 21 projecting'therefrom, and steam under pressure and at suflicient temperature to, fuse the` adhesive between-the vstrips is yadmitted to the chamber 22. -By reason ofthe iiexibilityof the'rubber bag 20, the' pressure apvplied thereto squeezes Athe overlapping strips together and the heatjsimultaneouslyv causes them tto, be; bonded together. vAir' and steam trapped j within-` the -bag 20 'is vented to` atmosphere y, through the pipes 2 I '-,The entire `bonding 'operv assass. ationA is. essentiallyy .the .same ffaslfthat described in 'theA patent tol Potchen' andBasquingNo'ff2'308 453;'datedJanuaryflZg'1943;- f.; l f After the? strips have-been bonded together-'in the manner described?, lthe"-'mar'1drelI iis-removed from the bag 20 vand collapsedQf-so tha'ttlie *fine void. ofi-the :surface elevations provided at .the

ished geodeticfuselage' structure 2 3' f be stripped therefrom;

YEither after or prior tostripping'tneffuseiage' shell 23y from -thefmandrel 10,' or priorita the bonding operation, the strips are securely and permanently Lfastened to the'f engineu bulkhead ring |4, f and Ptoy the tail bulkhead ring I if, `by means of rmetallicfas`teners or by means of jini terposed thermosetting adhesive; or thef like, depending upon requirementsfthe'tack's which were used to temporarilyfasten the stripsfthereto not interfering withthe permanent fastening oper- 1 forming the shape tol that-desired.

crossing. points of the strips,- the stripsfare' wound in the vsame way, but the-bonding pressure is applied from theinside against a smooth she1l,-so that theelevations areflocatedfon the inside sur'` face ofthe structure. Apparatus for conducting this method v is illustrated lin Figs. '6 to 8,L inclusive, which is` arranged for making a fgeodetic wing, although theapparatus .is equally adaptable tomakingfuselages and other parts .by con- As shown in Fig. 6, the form onwhich vthe strips 24 are wound comprises a heavy -innatable ation.' When'k intermediate bulkhead ringsl are,

employed the stripsv may likewise` lbe tacked to them as they'are wound over thev mandrel? and thermosetting adhesive may be-"interposedbetween'4 thefirst and'second layers |8j'and19* and ythe surfaces'of the buikheads, so-thatthe strips are likewise bonded to the: bulkheads, 'p'

Asillustrated in Figsfl` and l5,-the structure thus-formed is essentially' homogeneous, evenj at the juncture of the strips; iny view of thescaring of the edges thereof; so Athatthe're are no sharp rcorners over which `theiibres of the wood would be sojsharply bent as to break orfinjure them.

I `The thermosetting adhesive penetratesthe wood to al substantiai depth, so that the strips are se'. curely and permanently bonded togetherwith uniform strength over everyunit of area of y'overlapping strips. lTypical-sectionsthrough the gethickened root ende wan 2a of" bag 25 having the airfoil contour in chordwise Icross' section land blunt root and Wing tip'ends.

The bag 25 is preferably of rubber, either natural or synthetic,v and' hasformed'in its outer surface the grooves or vch'annels 26 crossing each other diagonally at rightangleain Awhich the strips are adapted tofbe placed'and which-"also serve as winding' guides in'lieu of `the pins I1 shown in Figl. f, A steam inlet nipple 21,'is secured through the the bag 25y-and aA metal clamp- `'which hold the root bulkin proper relation tothe surfaces of the This bulkhead 3| ispreferably'built up this nipple also cooperates with plate r29 and nut head 3| bag 25.`

of. plywood, and serves'as a, ynailing base for the strips 24.'. A similar arrangement for the wing odetic structure thusforr'ned are illustrated Figs. 4 and 5, which areself-explanatory.y The stresses and strains are distributed 'substantially uniformly throughoutt thestr'ucture' 23. -those along one diagonal being transferred 'to the next `'vice versa. 'asjis indicated crossing diagonal, and byxthe arrows in Fig. 3; If desired, the geodeticfuselageshell 23: so

formed, either prior vtofor after bonding', may

have applied thereto fabric 'or thin `wood,'ffibre,

or 'metal layer; riot'showm Where fabric; wood; or fiber covering is used, it may' be applied rbelk fore the bonding operation, andthe surfaces rof outer wood strips I8" and l9` coated with'thermosetting 'resin or other adhesive, so that' the covering may be bonded theretoY during" and simultaneously `with the final strip-bondingoperation within the bag zu in the manner yde-gv scribed. Metal covering maybe appliedinany suitable'way, such as byutilizing fastening means, such' as wire loops or 'rnetal'cleats passing around the crossed points ofthe strips and secured to the covering. These or any other forio of covering maybelapplied to the'innerfsurface of the fuselageshell 23 `after it'hasfbeen* stripped lfrom the mandrel, or during .its'fabrication by` covering the mandrel I0 with the'c'overingmaterial 'and building up the strips directly' thereon,

the lower lsurfaces of the strips l'and I9 vbeing Abag 20, as described. Bulkheads additional to `I4 and ,|5 may also besecured in `f place within the shell 23 afterithas been stripped from the mandrelfonthe purposeloffattaching wing4 spars that the strips f Whereit isl desired toproduce ageodeticstrucf tuiexhavinglaf smooth lexternalsurface, .-i.A 4.et de.- f

- small purging bypasf pipe Myand'yalvefqare provided in air pipe 38.; 1

In utilizing the apparatus shownin Figs. 6to 8, the bulkheads 3l and4 32,y and thefalse spar 40 are positioned as' described, 'and with steamvalve closed, air under pressure is admittedfto the inneeded, as the bag25 should not bulge outiof shape. Thenk the air 'valver 39 vis closed andthe stripwinding operation. proceeds as before except uppermost; and' the syntheticfresin adhesive 'is provided on the upper' or outer surface-of lthe f strips ofthe rst or'lowerrnostlayer and on the lunder surfaces of the strips of the layers following the second layer, which requires no adhesive o'nfeither surface vAlternatively; sheets of adhesive maybe laid between ,the Aseveral layersfof strips' 24. The strips `24 as woudare tacked to *the bulkheads`3l and 32 and t0 spar 40.

' After ,the requisite number oflayersiof'strips 24 havebe'en Wound in the grooves 2E ofthe rubber bag f25,"`a rigid sheet metal' 'diel is placed around the" whole assembly,Y this die' havingl the exact contour desired for the finished structure and having a smooth interior surface. AAsshcwn in Fig. 'l-the die 4| may be conveniently made in two sections 4hinged together at 42 and clampedy in place by-hin'ged bolts43. t ,I

Heat and pressure are then applied to this strip The false rear.

serves as a nail-- f ter'iorof rbag 25 to.ca1 1se thesurface thereof to `be firm during Winding.. Only'a few lpounds of pressure, such Iastenuto fifteen pounds gage jare 24 arelaid with their flat surfaces Y assembly byv opening steam valve 36.` Immediately thereafter air purge valve 45 is opened to vletnont the air. and. thisralveisle, Caper; uatilsteempe crossing strips in the Ying strips of intersecting gins to issue from pipe 44. In this way sufficient steam pressure is built up to preclude collapse of the bag 25 and consequent possible disarrangement of the strips while the air is being let out. With valve 45 shut, the steam pressure continues to build up to cause bag 25 to force the strips against the smooth shell 4l, so that by the time the apparatus is heated sufliciently'to cause the thermo-responsive adhesive to soften, the strips 25 are in the proper bonding relation shown in Figs.l 4 and 5, except inverted, the flat `surface being' directed outwardly.r

After the adhesive has performed its bonding function, steam valve 36 is closed and valve 45 reopened to purge the steam from the bag 25, thus relieving the pressure on the die 4|which may then be opened. The collapsed bag 25 is withdrawn through the opening in the root bulkhead 3I, after the plates 29 and' 33 are removed and the pipes 35 and 38 uncoupled from respective nipples 21 and 34. The finished geodetic Wing structure remains, which may then be fitted with additional chordwise bulkheads if desired, with a spanwise spar or spars, and with a metallic, fabric, fibre, or plywood skin covering.

The skin may be applied by overlaying the form therewith after Vthe winding of the strips 24 has been completed. Where fabric, fibre, or plywood isused, the outer or the rst two layers are coated with the adhesive resin and the covering laid thereover before the die shell 4l is applied. The heat and pressure will then simultaneously bond the covering and strips together.

' Although the invention has been illustrated and described in connection with the making of a fuselage and wing shells of th'e novel geodetic construction described, it is to be understood that the invention is not limited thereto but` is equally applicable to the manufacture of other parts by winding molds or forms with manner described and bonding them together. Also, the invention is not limited to the particular structure and mode of manufacture thereof limited by the scope of I claim: n

1. Themethod of fabricating a structural assembly, which comprises, superimposing thin strips of material to form bands arranged in sets of spaced bands; laying the strips .of bands of one set in a directionintersecting the bands` of another set; superimposing at intersections the strips of one band alternately with the strips of the respective intersecting band; exing the several strips of each band into surface to surface engagement with each other between intersections; attaching surface to surface the intersectbands at intersections; attaching surface to surface the strips in Aeach band between intersections; forming the several bands to a predetermined surface contour on one side of the assembly, and on the opposite side of the assembly forming them to a surface contour which is irregular in accordance with the degree of flexing of strips between intersections.

2. The method of fabricating a structural asthe appended claims.

-sembly of molded wood, which comprises, superimposing thin strips of Iwood to form bands arranged in sets of spaced bands; laying the strips of bands of one set in a direction to intersect the bands of another set; superimposing at intersections the strips of one band alternately with the strips of the respectiveintersecting band; flexing the several strips of each band into surface to surflat surfaces of the strips of l described herein except 'as r face engagement with each other between intersections, forming the severalbands to a prede-V termined surface contouren one side of the assembly, and on the opposite side of the assembly forming them toa surface contour which is irregular .in accordance with the degree of flexing of strips between intersections; attaching surface to surface the intersecting strips of intersecting the overlapping and y bands at intersections; and attaching surface to surface the strips in each band between intersections. A

3. The method of fabricating a structural assembly of molded material which com-prises, superimposing on va body of predetermined contour strips of thematerial to form intersecting bands; superimposing at intersections the strips of one band alternately with the respective strips of the intersecting band; pressing the bands against said body to force into surface to surl face engagement the strips of each band between intersections, to force into surfacel to surfaceengagement with one another the intersecting strips of intersecting bands at intersections and to flex the bands into conformity with the contour of said body; and adhering together the several engaged surfaces.

4. The method of fabricating a structural assembly which comprises, superimposing a plurality of thin strips of material to form bands; laying the strips of one or more bands in a direction to intersect one or more other bands; superimposing at intersections the strips of one band alternately With the strips of the respective intersecting band; placing a rigid mold having a contour corresponding to the desired contour of the finished assembly on one side of the intersecting bands; applying pressure to the opposite side of the intersecting bands against the mold to force into surface to surface engagement the strips of each band between intersections, to force into surface to surfaceengagement with one another the intersecting strips of intersecting bands at intersections, and to flex the several bands against the rigid mold; and adhering together the several strips along the engaged surfaces.

5. The method of fabricating a structural assembly of molded Wood which comprises, superimposing on aninflatable hollow member a plurality of thin strips of wood to form bands; laying the strips of one or more bands in a direction to intersect one or more other bands; superimposing at intersections the strips of one band ,alternately with the strips of the respective intersecting band; placing a rigid forming mold -over the laid strips; inflating the inflatable member to apply pressure to the assembly against sections, to force into surface to surface engagement with one another the intersecting strips of intersecting-'bands at intersections,` and toV flex the several bands against the rigid mold; and adhering together the several strips along the engaged surfaces.

6. The method of fabricatinga structural assembly, consisting of bands and a spar member, the method comprising, superimposing a plurality of .thin stripsl of vmaterial to form bands arranged in sets of spaced bands;V laying the strips of bands of one set in a direction intersecting the bands of another set; superimposing at intersections the strips of one band` alternately with the strips of the respective intersecting bandjattaching the ends of the "several bands to nthe spar member; flexing. the several strips of each band into surfacev to surfacey engagement tersecting bands alternately superimposed, the strips of intersecting bands at intersections, and thestrips in individual bands between intersections, being adhered together in surface to surface `engagement with each other, the several bands being formed t constitute portions of a smooth predetermined surface contour on one 7. A structural assembly, comprising a set of spaced bands intersectinga second set of spaced bands, each band of each set comprising a plurality of superimposed strips, the structure of each intersection comprising strips of the respective intersecting bands alternatelysupermposed, the strips of intersecting bands at intersections, and the strips in individual bands between intersections, being attached together in surface to side of the assembly, the bands forming an ir-` regular surface contour on the opposite side of the assembly determined by the total thickness of the superimposed strips vat each particular ppoint.

10. An airplane wing construction of moldedr wood comprising a spar member disposed longitudinally of the wing structure; a bulkhead at Y each vend of the spar member; and a. plurality surface engagement with each other, the several bands being formed to constitute portions of a smooth predetermined surface contour on one side of the assembly, .the bands forming an irregular surface contour on the opposite side of the assembly determined by the total thickness of the superimposed strips at each particular point.

8. A structural assembly of molded wood, comy prising a set of spaced bands intersecting a second set of spaced bands, each band of each set cornprising a plurality of superimposed strips, the several strips having their longitudinal edges feathered, the structure of each intersection ycomprising stripsfof the respective intersecting bands alternately superimposed, the strips of l intersecting bands at intersections, and the strips in individual bands between intersections, being adhered together in surface to surface engagement with eachother, the several bands being joined to constitute portions of a' smooth predetermined surface contour on one side of the assembly, the bands forming an` irregular surface contour on the opposite side of the assembly determined by the total thickness of the superim posed strips at each particular point.

9. An airplane Wing construction of molded Wood comprising, a spar member disposed longitudinally of the wing structure; and a plurality of bands arranged in sets of spacedbands, a rst set of spaced bands intersecting a second set of spaced bands at intersections, the bands being attached to and terminating at the spar member, each band of each set comprising a plurality of superimposed strips, the structure of each intersection comprising strips of the respective inof bands arranged in sets of spaced bands, a first set of spaced bands intersecting a second set of spaced bands, some bands being attached to and terminating at the spar member, remaining bands being attached to and terminating at a bulkhead, each band of each set comprising a plurality of superimposed strips, the structure of each intersection comprising strips of the respective intersecting bands alternately superimposed, the strips of intersecting bands at intersections, and ther strips in individual bands between intersections,

being adhered together in surface to surface engagement with each other, the several bands be` ing formed to constitute portions of a smooth predetermined surface contour on one side of the assembly, the bands forming an irregular surf face contour on the opposite side of the assembly, determined by the total thickness of the.

superimposed strips at each particular point.

11. The 'methodof fabricating a structural asy sembly which comprises, superimposing thin strips ofmaterial to form bands, laying the strips of one or more bands in directions to intersect one or more other bands; superimposing at intersections strips of one band alternately with strips of the intersecting band, flexing the sev- 1 eral strips of each band into surface to surface engagement with each other between intersections of bands, attaching the strips of intersecting bands at intersections, and the strips of each band between intersections, into surface'to surface engagement, forming the several bands to a predetermined surface contour on one side of the assembly, and on the opposite. side of the assembly forming them to a surface contour which is irregular and determined by the totalthickness of the superimposed strips at each particular point.

WILLIAM H. SCHWEBEL. 

